MODEL FUSELAGE CRASH IMPACT STUDY.
Abstract
This study demonstrates the accuracy and efficiency of an analytical method for predicting crash impact effects on fuselage structure. A digital computer program, developed as a tool for improving the crashworthiness of fuselage structure was used to predict the impact effects on model fuselage test specimens. Crash impact tests of these models then provided actual data for correlation with the analytical predictions. The analytical versus test comparisons showed good agreement. Fuselage bending moments, vertical decelerations and lower shell deformations were compared. Both the analytical and test result data plots of moments and decelerations show the high frequency and fundamental vibratory modes. The data indicates that the analytical method provides accurate predictions of fuselage response to crash impact and that the method can be a valuable tool in the design of crashworthy fuselage structure. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Apr 01, 1969
- Accession Number
- AD0687772
Entities
People
- D. L. Greer
- J. D. Weber
- T. L. Heid
Organizations
- General Dynamics